Method of monitoring the landing phase of an aircraft

1. Method of monitoring a landing phase of an aircraft comprising means for generating alerts monitoring a provisional landing distance and a configuration of the aircraft throughout the changes in the landing phase maneuver, these means comprising an onboard navigation system, performance databases, meteorological measurement sensors and data acquisition means, comprising the following steps; a. determination of sub-phases forming the landing phase, from a runway approach phase onwards, in order to monitor the configuration of the aircraft and the flight parameters with each of the sub--phases, b. determination of a runway status condition by means of data originating from a plurality of meteorological measurement sources, a number of sources changing throughout an execution of the landing sub-phases, the meteorological measurement sensors being retained to determine the runway status conditions, and c. calculation of the provisional landing distance according to a braking performance chart comprising input parameters, runway status parameters, flight parameters and aircraft configuration parameters, the landing distance being re-assessed according to a trend of the input parameters throughout the changes in the landing sub-phases.

2. Method according to claim 1 , wherein the method determines the following sub-phases: a first approach sub-phase before the landing gear is released, a second sub-phase preceding the overfly of the runway, a third sub-phase of overflying the runway preceding contact with the ground and a fourth sub-phase until the ground speed of the aircraft becomes less than approximately 50 kts.

3. Method according to claim 2 , wherein, during the fourth sub-phase, the runway status conditions are re-assessed by means of a performance chart according to a measurement of a deceleration and a ground speed of the aircraft, the performance chart defining a deceleration value according to the ground speed and runway surface status profiles for a given braking mode.

4. Method according to claim 3 , wherein, from the second sub-phase and to determine a landing runway, a runway data of the airport data in the on-board navigation system are compared with a location data of the aircraft and a ground speed vector data of the aircraft.

5. Method according to claim 4 , wherein, as soon as the aircraft overflies the landing runway, the runway surface status is re-assessed by a meteorological measurement of the runway surface status performed by an on-board measuring device positioned under the aircraft.

6. Method according to claim 1 , wherein the means for generating alerts detect an engine thrust dissymmetry.

7. Method according to claim 6 , wherein the means for generating alerts signal that the engine speed is too high for the aircraft to perform the third landing sub-phase in conditions of safety.

8. Method according to claim 7 , wherein the means for generating alerts warn of a braking dissymmetry when the aeroplane is of the ground.

9. Method according to claim 1 , wherein alerts inform that the aerofoil configuration does not conform to the current landing sub-phase.

10. Method according to claim 1 , wherein, for the calculation of the landing distance, the configuration parameters of the aircraft include the activation of the thrust reversers.

11. Method according to claim 1 , wherein, for the calculation of the landing distance, the configuration parameters of the aircraft include the aerofoil configuration.